space launch system - applied physics...

SPACE LAUNCH SYSTEM

National Aeronautics and Space Administration

www.nasa.gov/sls

5 . . . 4 . . . 3 . . . 2 . . . 1 . . .

Exploration Class Capability for

Deep Space Exploration

Bob Hawkins Deputy Lead Engineer

SLS Integrated Avionics and Software

www.nasa.gov/sls 0038_Flight Software.2

www.nasa.gov/sls

SLS Driving Objectives

Safe • Human-rated to provide safe and reliable systems

• Protecting the public, NASA workforce, high-value

equipment and property, and the environment

from potential harm

Affordable • Maximum use of common elements and existing

assets, infrastructure, and workforce

• Constrained budget environment

• Competitive opportunities for affordability on-ramps

Sustainable • Initial capability: 70 metric tons (t), 2017–2021

‒ Serves as primary transportation for Orion and

human exploration missions

• Evolved capability: 105 t and 130 t, post-2021

‒ Offers large volume for science missions and payloads

‒ Reduces trip times to get science results faster

‒ Minimizes risk of radiation exposure and orbital debris impacts

Designed for BEO Missions of National Importance

0038_Flight Software.3

www.nasa.gov/sls

• SLS initial

configuration offers

Block 1 to LEO.

• Future configurations

offer Block 1B and

Block 2 to LEO.

• More mass-to-orbit

means larger

payloads to variety

of destinations.

Medium/Intermediate Heavy Super Heavy

100’

200’

300’

Retired

Retired

ULA

Atlas V 551

SpaceX

Falcon 9

ULA

Delta IV H

NASA

Space Shuttle

NASA

Block 1

NASA

Block 2

NASA

Saturn V

0

20

40

60

80

100

120

140

160

Paylo

ad

Mass (

mT

)

Mass (mT)

SLS Mass-to-Orbit Comparison


www.nasa.gov/sls

Europa Trajectory Comparison

Launch (6/5/22)

JOI (5/23/24)

DSM (7/10/22)

VGA (5/14/22)

EGA-2 (10/24/25)

EGA-1 (10/24/23)

Jupiter’s

Orbit

JOI (4/4/28)

Launch (11/21/21)

Atlas V 551: VEEGA SLS: Direct

Reduces Transit Time To Europa By Half


www.nasa.gov/sls

SLS Evolution Overview

365 ft.

RS-25 Engines

364 ft.

Core Stage Core Stage

322 ft.

SLS Block 2 Cargo

130t

Interstage

Advanced

Boosters

Solid

Rocket

Boosters

Exploration

Upper Stage

327 ft.

SLS Block 1

70t

Orion

Launch

Abort

System

Launch Vehicle

Stage Adapter

Interim Cryogenic

Propulsion Stage

Exploration

Upper Stage

Cargo Fairing Cargo Fairing

Interstage

Universal

Stage Adapter

Solid

Rocket

Boosters

Core Stage

SLS Block 1B Crew

105t

SLS Block 1B Cargo

105t


www.nasa.gov/sls

SLS Block 1 Key Design Features

SLS Block 1 Crew

Launch Vehicle

Stage Adapter

Core Stage

and Avionics

RS-25

Engines (4)

Orion Stage Adapter

Solid Rocket

Boosters (2) Interim Cryogenic

Propulsion Stage

Orion Multi-Purpose

Crew Vehicle


www.nasa.gov/sls

Five-Segment Solid Rocket Booster

Qualification Motor-1 (QM-1)

March 2015, Promontory, Utah SRB Forward Skirt Load Test May 2014, Promontory Utah

Booster Processing, Promontory, Utah

SRB Aft Skirt Avionics Testing September 2014


www.nasa.gov/sls

5-Segment Booster Test Video


www.nasa.gov/sls

RS-25 Core Stage Engine

RS-25 Adaptation Test, Stennis Space Center, January – August 2015

RS-25 Controller


www.nasa.gov/sls

Core Stage Progress

Pegasus Barge Renovation Complete

LH2 Dome Assembly at Michoud, July 2015

LH2 Structural Test Article (STA) Test Stand,

MSFC, August 2015

B-2 Test Stand at Stennis Space Center


www.nasa.gov/sls

SLS MAF/Stages Progress Video


www.nasa.gov/sls

Spacecraft/Payload Integration and Evolution

Orion/MSA Mated to Delta IV for EFT-1 November 2014

DCSS for EFT-1 KSC, June 2014


www.nasa.gov/sls

Systems Engineering & Integration

Booster Separation Tests, LaRC October 2014

Base Heating Tests CUBRC,

Buffalo, New York January 2015

SMAT Testing, MSFC August 2014

Core Stage Engine TVC

Actuator Testing Redstone Test

Center March 2015


http://www.nasa.gov/sites/default/files/thumbnails/image/img_0419_blur.jpg

www.nasa.gov/sls

SLS Avionics Progress


www.nasa.gov/sls

Where is SLS Avionics Located?

Launch Vehicle Stage Adapter

(Two Cameras for ICPS Separation)

Core Stage Avionics

(Flight Computers, Command and Telemetry Controller,

Inertial Navigation Equipment, RF Transmitter)

Booster

Avionics Interim Cryogenic

Propulsion Stage

Avionics

Core Stage Avionics

(Command and Telemetry Controller, Power Distribution,

Data Acquisition, Camera Equipment, Liquid Level Sensors,

Rate Gyro, RF Transmitter)

Core Stage Avionics

(Main Propulsion System Valve Control,

Core Stage Thrust Vector Control, Rate Gyro)

Core Stage Engine Controllers

Booster

Avionics

SLS Block 1 Crew


www.nasa.gov/sls

SLS Block I Avionics Architecture


www.nasa.gov/sls

SLS Block I Software Providers

System: Flight Computer (FC)

Type: Byzantine Fault Resilient

3 String Voting Architecture

Developer: MSFC In-House

Category: Flight Critical

Function: Primary SLS Vehicle Flight

Control System

System: Redundant Inertial Navigation Unit (RINU)

Type: Internally Self-Checking Architecture

Developer: Stages Subcontractor (Honeywell)


Function: Provide Navigation and Flight Control

inputs to FCs

System: Rate Gyro Assembly

Type: Internally Self-Checking Architecture

Developer: Stages Subcontractor (Honeywell)


Function: Provide vehicle rate inputs to FCs

System: Core Stage Engine Controller (CSEC)

Type: Self-Checking Pair of Pairs (Prime/Backup)

Developer: Engines Contractor - Aerojet Rocketdyne (AR)


Function: Control/Monitor of RS-25 Engine

System: ULA Common Avionics

Based

Developer: ULA

Function: Primary ICPS Flight

Control and Health

Monitoring


www.nasa.gov/sls

SLS Block I Avionics and SW Test Labs

SDF-3

(FC FSW)

SITF-D (Stages)/

SIL(Level 2)

SITF-Q

(Stages)

SDF-1&2

(FC FSW)

Control

Room Booster

SITF-D/SIL

SITF-Q HIL


www.nasa.gov/sls

Path to EM-1 (First Launch)

2011 2012 2013 2014 2015 2016 2017 2018

Concept Studies

Design & Development Final Design & Fabrication

System Assembly, Integration and Test, Launch Checkout

✔ ✔ ✔ ✔ Mission

Concept Review

Critical

Design Review Preliminary

Design Review

Design

Certification

Review

Launch

Availability System

Requirements

Review/System

Definition Review

Key

Decision

Point-C

Booster

Development

Test

Booster

Assembly

at KSC

Booster

Qualification

Tests

RS-25

Flight

Testing

Begins

Core

Stage

Assembly

Complete

Core Stage

Production

Begins

Production

of Adapter

for Orion

Flight Test

SLS

Design

Chosen

RS-25

Development

Testing

Begins

Engines

Delivered

to

Inventory

Manufacturing

Tooling

Installation

Core

Stage

Structural

Testing

Boosters

Fabrication

Complete

With design and development work

mostly complete, the SLS Program is

now building and testing components

of the world’s most powerful rocket to

be ready for launch in 2018. Each of

these steps advance NASA on the

Journey to Mars.

Core

Stage

Test-Firing

✔

Integrated

Upper

Stage

Structural

Testing

Upper

Stage

Production

Begins

SLS

Launch

Readiness


www.nasa.gov/sls

Summary

SLS provides capability for human exploration missions.

– Block 1 configuration enables initial flight tests.

– Evolved configurations enable missions including humans to Mars.

SLS offers unrivaled benefits for a variety of missions.

– Block 1 provides greater mass lift than any contemporary launch

vehicle; Block 2 offers greater lift than any launch vehicle, ever.

– With 8.4m and 10m fairings, SLS will over greater volume lift capability

than any other vehicle.

– Updated Mission Planner’s Guide provides capabilities information.

SLS is currently on schedule for first launch.

– Critical design review completed in July 2015;

SLS is now in implementation phase.

– Manufacture and testing are currently underway.

– Hardware now exists representing all SLS elements.

SLS will be the Biggest and Most Capable Rocket ever Built


www.nasa.gov/sls

Questions?


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